Aeroplane



May 6, 1930. J. T; RYDBERG 1,757,879

- AEROPLANE Filed Nov. 8, 1928 2 Sheets-Sheet 1 INVENTOR W|TNE55ES fa/Z 71 fffydliely I J. T. RYDBERG May 6, 1930.

AEROPLANE Filed Nov. 8, 1928 2 Sheets-Sheet 2 TI' ZW By y ATTORNEY WITNESSES Z/M /w Z w ,jl/jttvf Patented May 6, 1930 UNITED STATES JOHN T. RYDIBERG, OF HARRISON, NEW JERSEY AEBOPLANE Original application filed December 2, 1927, Serial No. 238,869. Divided and this application filed November 8, 1928.

This invention relates to aeroplanes, the subject-matter of the present application having been divided from my co-pending application, Serial No. 238,369, filed December Among the objects. of the present invention is to provide an aeroplane well equipped to meet all types of weather conditions, particularly a plane which is adapted to be highly eflicient when flying in sleet and snow, in that novel means is provided for preventing the sleet and snow from collecting upon the wings of the plane and destroying the proper balance of the plane.

' Other features of the invention are the provision of a unique method of utilizing the engine exhaust gases for heating the body of the plane and for assisting in preventing the formation of ice, or of the depositing of snow upon the plane wings.

Further objects of the invention are to provide a plane embodying a plurality of prime movers some of which are located on the wings, and to so construct the wings of the plane that such prime movers are readily accessible for purposes of attendance and repair.

Other and further objects of the invention are to provide an aeroplane of extremely simple and practical construction which will be rugged, durable and efficient in use, and well suited to the requirements of economical manufacture and convenient manipulation.

More specifically, the invention contemplates the provision of a relatively 'gantic amphibian air liner in'which the b0 y simulates, to a large extent, the body of a bird, and

the wings simulate in so far as is practical, the

general shape of a birds wings. A body thus constructed aifords the desired streamline effect and by the provision of suitable keel mechanism is unusuallg easy to handle when landingl or taking 0 particularly when landin on, or rising from the water. The body and wings as noted above utilize Serial No. 818,049.

the engine exhaust for heating purposes: The wings are so constructed thatthey need no supplemental bracing or strut means to connect them to the body, being self-sustaining against lateral stresses. They are sufiiciently capacious to serve as storage spaces, and sufliciently rugged to stand up under the unusual excess loads imposed upon them.

With the above noted and other objects in view, the invention consists in certain novel features of construction and combinations and arrangements of parts, as will be more fully hereinafter set forth and pointed out in the claims. The invention may be more fully understood from the following description in connection with the accompanying drawings, wherein-- Figure 1 is a top plan view of an aeroplane embodyin the invention;

Fig. 2 is a longltudinal section through that form of the device shown in Fig. 1;

Fig. 3 is a transverse section through the wing of the device shown in Fig. 1;

Fig. 4 is a fragmentary perspective detail showing the oil distributing and heating pipes embodied in the wing structure;

Fig. 5 is a similar view illustrating a slight modification.

The general shape of the body may be I best seen from Figs. 1 and 2. As suggested above the body follows in a general way the shape of a birds body, but for practical purposes, this shape has been more or less conventionalized. The body is of general elon ated formation, preferably rectan .94" lar in cross section with a' substantia y straight flat or rounded top 10 and with a pointed nose 11 disposed well above the maor longitudinal axis of the body. From the nose 11 the breast 12 of the body slopes rearwardly to a relatively short substantially flat bottom 13. The tail 14 on its ufipsr surface is a continuation of the flat dy top, and on its lower surface inclines ually upwardly from the rear end 0 the 0 body at the bottom thereof.

relatively short fiat bottom 13. This lower inclined surface of the tail 14 is formed with a plurality of inclined steps 15 adjacent the forward end of the tail for a purpose which will be more fully hereinafter discussed.

The body is, of course, hollow, and referably inherently buoyant, although I ave shown the use of supplemental buoying means in the nature of waterti ht air compartments 16 running longitudinall of the A ditional buoyancy is lent by the hollow longitudinally extending keels 17 depending from the bottom of the body at each side edge. For stabilizing purposes the keels 17 are supplemented by a solid counterbalancing keel 18 centrally arranged. Both the hollow keels 17 and the central keel 18 are extended rearwardly at least as far as the uppermost of the steps 15. When the aeroplane is taking off from the water, and its nose is pointe upwardly, the various steps 15 with their associated stabilizing keels, will effectively maintaining the body against rolling and materially assist in the take-ofi. The step formation also serves somewhat in the manner of an aquaplane to assist in elevating the body when the latter starts to lift under its own power.

The device is preferably of the monoplane type including a single re atively large wing 19 secured to the top of the body adjacent the forward end of the latter. This wing due to the interior bracing indicated at 20, is selfsustaining against lateral stresses, and no supplemental bracing means or guy means need be employed between wing and body.

Carrying out the general streamline effect of the body, the top of the plane from the nose l1 inclines upwardly in a gradual slope at 21, and merges with the convexly curved upper surface of the wing 19.

The wings are preferably substantially flat bottomed and convex topped as seen in the sectional Fig. 3 and are of gradually decreasing thickness toward their tips. This decrease in thickness is accentuated by rather sharply inclining the under surface of the wings upwardly towards the tips, thereby producing in a conventionalized form the general shape of a birds wings.

Instead ofusing a single rudder as is customary, I mount a pair of co-operating rudders 22, one at each side of the tail of the plane, these rudders being hung on the usual fins 23 and controlled in a conventional manner (not illustrated). The usual laterally projecting stabilizers 24 are also employed at the tail of the plane.

An auxiliary lifting surface and balancing means is utilized in the nature of a. pair of supplemental wings or stabilizers 25 projecting laterally from the top of the body rearwardly of the main wing 19. These stabilizers are provided in their rear ends with elevators 26 adapted to automatically function in righting the plane from a tail spin and serving to supplement the usual elevators 27 on the stabilizer 24.

I do not wish to restrict myself to any special arrangement of prime movers but have illustrated one practical arrangement in which five motors and associated propellers are used. Two motors 38 are mounted on the forward end of the body substantially at the nose of the plane. Two other propellers and engines 39 are mounted on the win one at each side of the body, while the fifti prime mover 40 is suitably supported on an enclosed housing 41 rising from the center of the wing.

The 'motors 38 are readily accessible through the body of the plane. With a view to gaining access to the motors 39, a ladder 42 leads from the pilots cabin through a hatchway 43 into the wing. This hatchway gives access to a longitudinally extending compartment 44 in the front of the wing, equi ped with a gangway 45 along which a mec anic may pass to either of the engines 39. From the gangway 45, he may also reach a ladder 46 leading upwardly throu h a hatchway 47 into the housing 41 imm iately beneath the engine 40.

he exhaust from the engines 38 may be passed through any suitable number of heating pipes 48 having as many branches or bypasses as necessary before passing out at 49 through the tail of the plane. The circulation of exhaust gases through the ipes 48 may be assisted by one or more ans 50, whereby the efliciency of the engines will not be retarded due to the backing up of exhaust gases.

Means is provided for preventing the collection orfreezing of moisture on the upper wing surface. This means consists of an a ertured oil pipe 51 disposed on top of tffe wing and extending longitudinally thereof at a point somewhat forwardl and below the highest point of the wing. oncealed within the wing and immediately beneath the oil pipe 51 is an exhaust pipe 52 discharging through the ends of the wing and connected to an exhaust header 53 from the engines 39.

In Fig. 5 I have illustrated a slight modification in which a steam pipe 52" mounted on the top surface of the wing serves to cradle and support an oil distributing pipe 51. Obviously, the device of Figs. 4'or 5 might be mounted at the leading edge of the wing, if desired.

In inclement weather, oil is introduced into the pipe 51 from any suitable source, preferably flowing gravitationally from a tank 54 in the chamber 41. This oil, heated by the exhaust pipe 52 escapes through the apertures in the pipe 51, some of it flowing gravitationally over the front of the wing,

to heat sal and most of it being blown back over the rear surface of the wing, thereby keeping the wing top both heated and oiled to insure against any deposit of snow or any freezing of moisture on the wing surface. Additional exhaust fans (not sho'wn) may, of course, be employed in connection with the pipe 52, if deslred.

From the foregoing description, it will be apparent that the device is well adapted for both land and marine purposes. Most of the conventional control mechanism has been avoided in order that the drawings may not be unduly complicated.

Obviously, various changes and alterations might be made in the general form and arrangement of the parts described without departing from the invention. Hence I do not wish to limit myself to the details set forth, but shall consider myself at libert to make such changes andalterations as airly fall within the spirit and scope of the appended claims.

I claim:

1. An aeroplane having a hollow wing, an oil distributing pipe su ported on the top surface of the wing an a heat conducting exhaust pipe mounted adjacent the oil pipe pipe.

2. An aeroplane having a hollow wing, an oil distributing pipe su ported on the top surface of the wing and a heat conducting exhaust pipe mounted under the top surface of the wing to heat said oil pipe, the top wing surface belng transversely convex and the oil pipe being disposed slightly forwardly of and below the crown of the wing.

3. The combination with an aeroplane wing, of means for distributing oil over the surface of said wing, and means associated therewith for heating the oil distributing means.

4. The combination with an aeroplane wing, of means for distributing oil over the surface of said wing, and means associated therewith for heating the oil distributing means, said first-mentioned means including an apertured oil discharge ipe.

5. The combination wit an aeroplane wing, of means for distributing oil over the surface of said wing, and means associated therewith for heating the oil distributing means, said first-mentioned means including an apertured: oil discharge pipe on the surface of the wing.

6. The combination with an aeroplane wing, of means for distributing oil over the surface of said wing, and means associated therewith for heating the oil distributing means, said first-mentioned means including an apertured oil discharge pipe on the surface of the wing, said second-mentioned means including an exhaust gas conducting pi e.

The combination with an aeroplane JOHN T. RYDBERG. 

